Aeroplane construction.



H. KLECKLER.

AEHOPLANE CONSTRUCTION. APPLICATION FILED IAII. I3. I9I6.

Patented Jan. 7,1919.

4 SHEETS-SHEET l.

' INVENTOIQ HENRY KLIKLIIa,

ATTORNEY MTW I Im mv m, NHL

om. @IT

H. KLECKLER. AEHoPLANEcoNsRucTIoN.

APPLICATION FILED 1AN.I3. |916.

Patented J an. 7, 1919.

4 SHEETSiSHEET 2.

@HAVANA x VOA Y UA IME-NTO?. HENRY KLECKLER ATTOIQN EY `H. KLECKLER.

AEROPLANE CONSTRUCTION.

APPLICATION FILED Patonted Jun. T, 1919.

4 SHEETSSHEET 3.

H. KLECKLER.

`AEROPLANE CONSTRUCTION. APLICATION FILED JAN. I3. 1916.

Patented Jan. 7, 1919' 4 SHEETS-SHEET 4.

/IVVE/VTOI? HENRY KLECHLEQ l ATTORNEY `itE @TATES OFFRE,

HENRY KLECKLER, OF BUFFALO, NEW YORK, ASSIGNOR, BY MESNE ASSIGNMENTS, T0-

CURTISS AEROPLANE AND MOTOR- CORPORATION, OF BUFFALO, NEW YORK, A.

CORPORATION OFVNEW YORK.

AEROPLANE CONSTRUCTION.

Specification of Letters Patent.

Patented Jan.- 7, 1919.

v Application filed January 13, 1916. Serial No. 71,892.

To all whom t may concern:

`New York, have invented certain new and useful Improvements vin Aeroplane Construction',.of which the following 1s a speciiication.

. VMy present invention relates to aeroplanes andA contemplates moreespecially, improve ments 1n' the construction of aeroplanes of draft system for the aeroplane which shall conduct the tractor pull rearwardly through longerons terminating in transverse alinementrwith the bed of the motor and to tie respective wings, through the medium of their posts, and suchadditional rigidcross bracing as may be desirable, directly to com- Amon portions of the draft bearing longerons.

Other objects also specifically concerned 4with an aeroplane of the mentioned type reside in the production 'of novel means for hinging the lower set of wings of a biplane cell directly to the fuselage; in lproviding fittings of a special nature for the fuselage; in permitting the accommodation of a fuel tank adjacent the engine bed by avoidance of the normally interfering framework of the fuselage; by arranging operating and control means for the flight governing surfaces and by'advancing a particular construction forv the ground skid of the fuselage.

Theabove and additional objects, to be hereinafter more specifically treated, are accomplished by such means as are illustrated in the drawings, described in the' following out in the claims, which are appended hereto specification and then more clearly pointed and forma part of this application.

l/Vith reference to the drawings, in 'which there is illustrated one embodiment of the invention, and throughout the several views of 'which like characters of reference designate similar parts, y A

Figure l is aside elevational view of the fuselage provided by the present invention, shown as stripped of its externals for the purpose of more clearly disclosing its con-- struction;

Fig. 2 is a plan view 'ofthe same subject matter; f

vsection I conengine section of the fuselage'of the preceding figures showing' `the fuel tank in vertical Fig. t'is a plan View of the preceding enlarged figure, showing a horizontal section through the fuel tank;

Fig. 5 is a view in perspective of the engine plate;

Figs. 6 and 6 are detail showings ofthe rudder foot bar disclosed in the assemblies of Figs. 3 and 4;

Figs. T and 8 are elevational y details of the fuelptan'k per se.

Aeroplanes of the tractor type employed by the present invention usually carry their power vplant forwardly in a fashion somef what similar to the customary automobile practice, for direct driving of the tractor blade. The' draft questioin'nainely that of applying the tractive effort of the motor.

developed through the propeller pull in such manner as to avoid waste in the transmis` sion ofthe power, involves the relation of the aerial supporting surfaces to the center of gravity of the machinein a fashion which will give a practical approximation of what may be termed the theoretical center of resistance7 and also involves the connection of the axis of pull provided by the tractor screw to the center of resistance thus practically determined. rlhese considerations are of major importance in determining a successful model of this type of aeroplane and such a draft question must-be solved in the fabrication of the fuselage.

The .present invention intends, accordingly, to provide a'fuselage for an aeroplane of this type in which the practical determii nation of a theoretical center of resistance is provided and in which' the motor and propeller mountings are such as to afford the best results in the connection of the axis of pull to this center.- In addition, a system of draftwiring in supplementation of the I usual lift and drift wiring has been pro'- vided.

The fuselage itself is mainly composed of a pair of upper longerons 25 and of lower longerons 26. The former are substantially horizontal in their normal extent from the tail post 27 forwardly to the fuselageengine section, beyond'which they are bent downwardly in the manner denoted by thev numeral 28 for attachment to the engine plate 29. The loiver longerons 26 are, how: ever, curved in tivo directions simultaneously; vertically from the engine plate to the tail post and horizontally tapering from the maximum beam of the fuselage' to the latter. Both the maximum vvidth and the maximum depth of the fuselage is attained at and intermediately behind the engine section thereof7 such engine section being deylined by forvvard fuselage posts 30 and similar rearward posts 31. Parenthetically, it may be remarked that. the term. engine sec-V tion is applied by custom to that part or portion of the fuselage to which the sup orting surfaces are directly connected, ovving to the old arrangement of suspending the motor also over the same portion of the fuselage. AAlthough the position of the motor has since been changed the name has persisted adesignation of this particular fuselage section..

Continuing the fuselage posts 30 and Bl of the engine section. then, are the tapering wing posts 32 which are alined with the former posts by means of socket fittings 33 engaging Athe upper longerons. It is Within this fuselage. section that the theoretical center of resistance is to be approximated in Aso practice.k For all practical purposes it may be considered that the center of resistance is located in the horizontal plane of the upper longcrons within the engine section. Connection of the center thus approximated With the engine plate :29 is the next consideration and while a variety of Ways suggest themselves, it is the object of this invention to provide this connection in the most si1nple and direct manner capable of accomplishing the objects sought. It is Afor this reason that the upper longerons Q5 are continued directly to the engine plate 29, to which they are fastened in alinement with the forward extremities of the engine bed beams 34, ears and 3G respectively cured to and angularly projected from the plate determining sockets for the beam and longeron extremities.' rllhe longeron extrem-- ities being thus arranged. reference being made particularly to Fig. 5, in direct lateral alinement with respect to the engine bed beams. it will be seen that the upper edge of the plate Q9 serves as the most direct possible connection of the propeller pull to the defined center of resistance. through the curved portions 28 of the upper longerons, and that the intervention of any auxiliary draft members. as offered in some other types is Wholly unnecessary. The propeller hub projects through the center of the plate as is provided for by the surrouiulingtiange 35a. Socket ears at vthe lower corner of the plate provide for the anchorage of the lower longerons 2G. Lightening holes are arranged at proper intervals through the 'that of the fuselage and also to the loiver plate and. are each rimmed with a bent-up flange for strength.

ltearu'ardly, the engine bed beams are supported upon a cross bar 37 which is mortis-ed into engine bcd posts 38 vertically connecting corresponding upper and lower longerons, of the fuselage, immediately foryvard of the engine section. A draft bar 39 obliquely connects each fitting B8 of the forward fuselage posts 30 to the rear portion of -wing panel et() through thermedium of the latters supporting Wing post 32. Wings (not shown) are hingedly attached to this panel which is of a Width corresponding to extremities of the posts 30 and 3l. Reaction stays 1Q are employed to tie the upper Wings both forwardly and rearwardly bach to the fuselage.v l

lt is understood that the speci-fic construe tion of the fuselage includes the customary connection of longerons 25 and 26 by means of vertical struts 43 and horizontal struts each of which is in turn. cross connected b v transverse bracing and by lift and drift wiring "l` he fuselage framework is covered with a suitable substantially frictionless skin on the sides and bottom, While covvls 46 and t? cover respectively the engine and the passenger sections, a rear cover 4.8 protecting the tail portion of the fuselage between the last named coivl and the fixed stabilizing surfaces. These latter are directly supported upon the upper longerons and include the usual horizontal stabilizer 4.9 and the vertical fin 50. To the former are hinged the movable ele fators 5l While upon the latter the rudder' 52 is mounted7 to provide the customary controlling surfaces.

rEhe pilots controls have been illustrated A as of the Deperdussin type, including the aileron operatingY Wheel 53 which is mounted Within a fork carried upon the lever 55, such lever being mounted for fore and aft oscillation upon its shaft 56 for actuation of 110 the elevators 5l -throuefh the medium of the dexible connect-ions 5' extending betvveen each elevator and lever arms 58 carried at the extremities of the. shaft 56. Through flexible connections 59 the rudder 52 may be 115 operated by movement ofthe foot lever 60 which is supported upon a short platform fiooringm'ithin the pilots cockpit. The observer or passenger is provided with a seat G1 Within the engine section and in tandem 12@ alinement With the pilots seat 52 immediately therebehindl both of such seats being commonly supported by respective cross bars 63 upon the longitudinal bar Gel.

The. detail construction of the foot bar is well illustrated in Figs. 6 and 6a. in which the mounting base is denoted' by the numeral. 60a, and serves to support a. heavy projecting pin 6la which is also rigidly maintained by a bearing sleeve Za-I-intermediately sur- 30 rounding the pin andalso carried upon the base 60a. The bar 60 is mounted for movement upon the pin 61 and the sleeve 62a in conjunction so that an efficient mounting is provided \which is at the same time of a simple nature. A V-shaped brace 63 is secured as shown at 64a to the mounting platform at' the extremities of its spaced legs, the latter converging to anchor the exposed upper end of the pin 61a, some such means as thecotterpin illustrated being employed to maintain the whole for ready disassembly.

The positioning of the fuel tank in an aeroplane havino' .its motor arranged far forward is usually a matter of some difficulty, for while it is most desirable to place the fuel tank in immediate proximity .to

the engine, thisis'frequently interfered with by the fuselage framework in such manner that the tank whichrcould be introduced at the desired point would necessarily' be much reduced in size. The resent invention,

however, solves'this difficulty without loss of a desirable position of the tank, and without reduction inthe size thereof, by obviating any interference therewith of the adjacent fuselage framework. Referring now to Figs. 3-6 inclusive, the fuel tank 65 has been positioned immediately in the rear of the engine bed 34, projecting back into the engine section. The strut 66 which connects the upper extremities of the forward fuselage posts 30 is accommodated within a channel 67 formed entirely through the tank and rendered leak proof in any desirable fashion. The tank is formed of some light metal which is provided with ribbing 68 and equipped with agage float 69 of a customary character. A leak-tight recessing cap 70 is also provided in the forward facey `of the tank to accommodateJ engine parts rearwardly projecting beyond the limits of the bed 34.

In Figs. 7 and 8 there is illustrated in detail the method of supporting the tank, which does not devolve. upon the strut 66 projecting therethrough. Flanges 71 are carried in -lateralextension by the tank to overlie respective upper longerons 25 uponl which they are supported' through the mei dium of some cushioning means 711 of felt or somesimilar partially elastic fiber material. From the engine bed beams 34 there depend the stirrup straps 72 which are connected by transverse strips 73 completingl a cradle for the support of the forward lower end of the tank. The cradle is also .lined with the cushioning means 712L which thus prevents transmission of the engine vibration directly to the tank contents, although detracting in no way from a superior method of support. I

Referring again to Figs. 1 and 2 of the drawings it will be noted that the engine plate 29 functions not only as a rigid conof the fuselage as well as an element ofthe utmost importance in fuselage design.

In conclusion,- it may be noted that the running gear of the fuselage, whiley partakin'g of little individual novelty per se, has been arranged by this invention with particular regard to the draft system and to the generalfuselage arrangement. As will be remembered, 'the engine section as de-l finedy by the fuselage posts 31, comprehends a center of resistance in the plane of the upper longerons 25; the engine bed beams 34 determine an axis of pull which is connected directly to the fuselage engine section by means of the curved longeron portions 28 which serve to connect the engine plate 29 directly with the top ,of the-posts 38, this plate and these posts forming the support for the engine bed, while these longeron portions are integral continuations of.

the longerons 25 in the plane of which a center of resistance is determined. The running gear posts or beams 133 then complete thel inter-relating of these particular fuselage elements by converging from the fuselage posts 31 and B8-to a common support of "the axle '134 upon which the ground wheels 135 are mounted for shock absorbing movement relative `to the fuselage.

While in the foregoing, however, there has thus been illustrated in the drawings and described in the specification such combination and arrangement of elements as constitute one preferred embodiment of this invention, it is desired to emphasizethe fact that such departures from the particularembodiment disclosed may be -made in later adaptations of this invention -as shall be recognized as within the scope yof the appended claims.

What is claimed is: l.l In an aeroplane fuselage, longerons, an engine plate interconnecting the .forward extremities of certainof said longerons fuselage struts interconnect-ing upper and lower -longerons at a point rearwardly removed from said engine plate, a cross strut connecting said fuselage struts, and engine bed beams terminally supported respectively by the engine plate and cross strut.

-2. An aeroplane fuselage including longerons, an engine plate connecting corre-l I spending 'extremities of the longerons, and

t i ,senses an engine bffl supported at one end by said plate in transverse alinement with certain of said longerons. 4

3. An aeroplane fuselage including longerons, an engine plate connecting corresponding extremities of the longerons, posts intermediately connecting the corresponding upper and lower longerons, and an engine bed supported by said plate and said posts.

4. An aeroplane fuselage including longerens, fuselage posts connecting corresponding upper and lower longerons, an engine plate connectingl extremities of the longerons, engine posts connecting said upper and lower longerons between said plate and the fu-selage posts, and an engine bed supported by the 4second mentioned posts and said plate.

5. An aeroplane fuselage including longerons, fuselage posts connecting corresponding upper and lower longerons, an engine plate connecting the extremities of the longerons, said longerons at their extremities convergng from said posts, and engine bed beams supported at one extremity by said plate in the vicinity of the bent extremities of said longerons.

G. An aeroplane fuselage including lon gerons, fuselage posts connecting corresponding upper and lower longerons, wing posts continuing the fuselage posts, means rigidly connecting opposite extremities of the wing posts, and an engine plate connecting extremities of said longerons in a verti cal plane forwardly removed from the plane of said fuselage and wing posts.

7. An aeroplane fuselage including lon-l gerons, posts connecting upper and lower longerons, a pla-te connecting longeron ex-` tremities, an engine bed partially supported by said plate,A posts connecting the longerons to further support said engine bed, and running gear beams secured to the sec- `ond said posts and to certaini of the first said posts for convergence below the fuselage. l

8. ln an aeroplane, the. combination Awith thev longerons of the fuselage and the beams of the engine bed, of an engine plate, and ears formed upon said plate to engagev said longerons and said beams respectively.

9. ln an aeroplane fuselage, the combination with a propelling power plant including in its ensemble a radiator, of longerons, and anengine plate mounted at theforward cxtremity thereof dually functioning as an interconnection between said longerons and as a radiator support. v

l0. In an aeroplane,v the combination with the longerons of the fuselage and 'the beams of the engine bed, of an engine plate, trans` versely alined pairs of ears formed upon said plate to engage the longerons, and transversely aliued pairs of ears formed upon. said. plate and inwardly removed from the ends thereof to engage said engine bed beams.

ll. ln an aeroplane, thc combination with the lower longerons of the fuselage, of engine bed beams mounted at the forward extremit)v of the fuselage, and an engine plate of substantially isi-form having its extensions in engagement with the engine bed beams and its bight in engagement with said longerons.

12. ln an aeroplane, the combination with the longerons of the fuselage and the beams of the engine bed, of a skeleton plate provided with lightening holes, and ears formed upon said plate to engage said longerons and said beams respectively.

13. In an aeroplane, the combination with the longerons, of the fuselage and the beams of the engine bed, of a skeleton engine plate provided with lightening holes marginally flanged to increase strength, the terminal portions of the plate being extended beyond the center portion thereof to provide an open space through which a portion of the engine may extend, ears formed upon said extended terminals to engage the engine bed beams, and ears formed adjacent the bottom marginal edge of said plate to engage the longerons.

la. ln an aeroplane, a fuselage framework, an engine bed contained within the framework, straps dependent from said engine bed, means connecting said straps, and a fuel tank arranged within the framework in juxtaposition to said bed and. partially supported by said straps. Y

l5. An aeroplane including a lfuselage framework, an engine bed contained within the framework, struts composing portions of the framework and a fuel tank mounted within the framework in juxtaposition with said bed and provided with passage ways therethrough to accommodate elements projec'ting from said bed and struts forming part of said framework.

16. ln an aeroplane fuselage, upper. and. lower longerons, an engine plate Connecting the forward extremities of the lower longerons at a point rearwardly removed from said engine plate, engine bed means sup ported at their forward extremity by the 

